Patents by Inventor Louis Veltre
Louis Veltre has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 9632011Abstract: A method of testing a gas turbine is provided. The gas turbine includes a first compressor and an expansion turbine coupled by a drive shaft. The method includes operating the gas turbine and a second compressor at a first steady load and a first steady drive shaft speed. The second compressor is rigidly coupled to the drive shaft. The method also includes changing a load of the second compressor by a known amount, and measuring a time required for the gas turbine to stabilize at a second steady load and a second steady drive shaft speed in response to the changed load of the second compressor.Type: GrantFiled: December 22, 2014Date of Patent: April 25, 2017Assignee: General Electric CompanyInventors: Jason Dean Fuller, Louis Veltre, Daniel Richard Waugh, Justin Aaron Allen, Paige Marie Sopcic, Maxime Buquet, Christian-Anghel Solacolu
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Patent number: 9255580Abstract: Certain embodiments of the disclosure may include systems, methods and apparatus for operating and validating a compressor. According to an example embodiment of the disclosure, a method is provided for validating compressor operation. The method can include receiving compressor operating parameter data from a plurality of sensors; and adjusting a portion of a variable flow area downstream of a compressor discharge to achieve a desired compressor pressure ratio.Type: GrantFiled: September 28, 2012Date of Patent: February 9, 2016Assignee: General Electric CompanyInventors: Daniel Richard Waugh, Karl Dean Minto, Scott William Szepek, Louis Veltre
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Publication number: 20150177106Abstract: A method of testing a gas turbine is provided. The gas turbine includes a first compressor and an expansion turbine coupled by a drive shaft. The method includes operating the gas turbine and a second compressor at a first steady load and a first steady drive shaft speed. The second compressor is rigidly coupled to the drive shaft. The method also includes changing a load of the second compressor by a known amount, and measuring a time required for the gas turbine to stabilize at a second steady load and a second steady drive shaft speed in response to the changed load of the second compressor.Type: ApplicationFiled: December 22, 2014Publication date: June 25, 2015Inventors: Jason Dean Fuller, Louis Veltre, Daniel Richard Waugh, Justin Aaron Allen, Paige Marie Sopcic, Maxime Buquet, Christian-Anghel Solacolu
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Publication number: 20140093349Abstract: Certain embodiments of the disclosure may include systems, methods and apparatus for operating and validating a compressor. According to an example embodiment of the disclosure, a method is provided for validating compressor operation. The method can include receiving compressor operating parameter data from a plurality of sensors; and adjusting a portion of a variable flow area downstream of a compressor discharge to achieve a desired compressor pressure ratio.Type: ApplicationFiled: September 28, 2012Publication date: April 3, 2014Applicant: General Electric CompanyInventors: Daniel Richard Waugh, Karl Dean Minto, Scott William Szepek, Louis Veltre
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Patent number: 8133030Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the TABLE. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: September 30, 2009Date of Patent: March 13, 2012Assignee: General Electric CompanyInventors: Andrew D. Grafitti, Louis Veltre, Thomas W. Vandeputte
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Patent number: 8011894Abstract: A sealing system for sealing a gap between a dovetail tab of a bucket and a rotor. The sealing system may include a sealing slot positioned about the dovetail tab and a pivot plate positioned within the sealing slot. The sealing slot may include a pivot point and a rest ledge such that the pivot plate pivots about the pivot point and into the gap when the bucket rotates.Type: GrantFiled: July 8, 2008Date of Patent: September 6, 2011Assignee: General Electric CompanyInventors: Brian P. Arness, Louis Veltre, Ariel Kelsey Coleman Harter, John D. Wardell
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Publication number: 20110076150Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the TABLE. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.Type: ApplicationFiled: September 30, 2009Publication date: March 31, 2011Inventors: Andrew D. Grafitti, Louis Veltre, Thomas W. Vandeputte
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Publication number: 20100008769Abstract: A sealing system for sealing a gap between a dovetail tab of a bucket and a rotor. The sealing system may include a sealing slot positioned about the dovetail tab and a pivot plate positioned within the sealing slot. The sealing slot may include a pivot point and a rest ledge such that the pivot plate pivots about the pivot point and into the gap when the bucket rotates.Type: ApplicationFiled: July 8, 2008Publication date: January 14, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: Brian P. Arness, Louis Veltre, Ariel Kelsey Coleman Harter, John D. Ward
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Publication number: 20080317597Abstract: A bucket for a turbine includes a dovetail mounting portion, a shank portion defined at a radially outer end thereof by a platform, and an airfoil portion extending radially outward of the platform. The airfoil portion has a radially outer end closed by a tip cap having a non-planar shape that reduces stress in the tip cap during use. A related method of reducing stress in a tip cap of a turbine bucket includes providing an airfoil portion of the turbine bucket with a radially outer end; and closing the radially outer end with a tip cap having a non-planar shape that reduces stress in the tip cap during use.Type: ApplicationFiled: June 25, 2007Publication date: December 25, 2008Applicant: General Electric CompanyInventors: Louis Veltre, William S. Zemitis, Gary C. Liotta
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Patent number: 7416391Abstract: In a turbine bucket having an airfoil portion and a root portion with a platform at an interface between the airfoil portion and the root portion, a platform cooling arrangement including: a cooling passage defined in the platform to extend along at least a portion of a concave, pressure side of the airfoil portion, at least one cooling medium inlet to said cooling passage extending from an airfoil cooling medium cavity in a vicinity of an axial center of the airfoil portion, and at least one outlet opening for expelling cooling medium from said cooling passage.Type: GrantFiled: February 24, 2006Date of Patent: August 26, 2008Assignee: General Electric CompanyInventors: Louis Veltre, Christopher Arda Macarian
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Publication number: 20080145227Abstract: A method of assembling a rotor assembly is provided. The method includes coupling a first turbine bucket to a rotor disk wherein the first turbine bucket includes a first tip shroud including a first surface, providing a second turbine bucket that includes a second tip shroud including a second surface, and coupling the second turbine bucket to the rotor disk such that the second turbine bucket is circumferentially adjacent to the first turbine bucket and such that during operation of the rotor assembly the first tip shroud contacts the second tip shroud along the first and second surfaces to enable at least one of a portion of radial loading induced to the first tip shroud to be transferred to the second tip shroud and a portion of radial loading induced to the second tip shroud to be transferred to the first tip shroud.Type: ApplicationFiled: December 19, 2006Publication date: June 19, 2008Inventors: Mark Stefan Maier, Robert Alan Brittingham, Louis Veltre
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Publication number: 20070201979Abstract: In a turbine bucket having an airfoil portion and a root portion with a platform at an interface between the airfoil portion and the root portion, a platform cooling arrangement including: a cooling passage defined in the platform to extend along at least a portion of a concave, pressure side of the airfoil portion, at least one cooling medium inlet to said cooling passage extending from an airfoil cooling medium cavity in a vicinity of an axial center of the airfoil portion, and at least one outlet opening for expelling cooling medium from said cooling passage.Type: ApplicationFiled: February 24, 2006Publication date: August 30, 2007Applicant: General Electric CompanyInventors: Louis Veltre, Christopher Macarian